A structure and corresponding method of manufacturing are described, where the structure is fabricated via additive manufacturing. The structure includes a plurality of sub-structures integrally formed via additive manufacturing. The plurality of sub-structures provides the structure with at least three load paths in an instance in which a load is applied to the structure and is thus capable of continuing to support the load following failure of one of the sub-structures. In some cases, at least one sub-structure is designed to arrest propagation of a material failure of the structure resulting from the load.

In one example, an article including a soft substrate defining at least one of a first outer perimeter of the substrate or an aperture extending through the soft substrate defining a second outer perimeter of the aperture; a hard coating on the outer surface of the soft substrate; and at least one reinforcement member extending through the soft substrate at a location adjacent to at least one of the first outer perimeter or the second outer perimeter, wherein the at least one reinforcement member increases resistance to compression of the soft substrate at the location of the at least one reinforcement member.

A plugged stringer on a surface of a part, and a method and assembly for production of the plugged stringer. The plug has opposite first and second axial end faces. The plug also has a radially outer margin defined by a radially outer bottom face, radially outer first and second opposite side faces, and a radially outer top face. The plugged stringer also includes a covering overlaying the radially outer top face and the first and second opposite side faces of the plug and extending away from the plug along an axis to form a stringer having first and second segments delineated by the plug. The radially outer margin of the plug is at least partly covered by an adhesive. The radially outer bottom face is adhered to the surface of the part, and the covering is adhered to the radially outer first and second opposite side faces and the radially outer top face. The first and second segments of the stringer respectively define first and second fluid passages separated by the plug. The first fluid passage is fluidly isolated from the second fluid passage by the plug.

A reinforcing element for a structural profile, in particular for a round, oval or elliptical structural tube. The reinforcing element comprises: a fiber structure which has a hollow-cylindrical, helically wound mesh of fiber strands and forms an inner shell surface formed to receive the structural profile; and a matrix material into which the fiber strands are respectively embedded and which is formed to be shrinkable by heating so that the fiber structure can be fastened to the structural profile with the inner shell surface by heating the matrix material. Also provided are a structural arrangement with such a reinforcing element, an aircraft or spacecraft with such a structural arrangement, as well as a method for producing such a structural arrangement.

Beaded panels and method of forming beaded panels. A beaded panel as described herein includes a base structure comprising a sheet of material, and beads that comprise a protrusion on a first side of the base structure, and a concavity on an opposing second side of the base structure. A geometry of the beads comprises a center section having a conic shape about a longitudinal axis, flared sections symmetric about the center section along the longitudinal axis, and a transition section that curves outward from a base of the center section and the flared sections to blend with a flat surface on the first side of the base structure.

An apparatus includes a foam layer, a coating layer and an elastomer. The foam layer includes a first surface for coupling the apparatus to a surface exposed to weather, a second surface opposite the first surface, and a plurality of pores within the foam layer. The coating layer is deposited on the second surface of the foam layer. The elastomer is deposited within the plurality of pores within the foam layer.

A method for installing a replacement electrical heat sensor in a heatable aircraft window laminate structure comprising the steps of: drilling a blind hole in the edge of the window laminate; routing a channel in the edge of the window laminate from the blind hole to a terminal block of an originally installed heat sensor; inserting the replacement heat sensor into the hole; filling the hole with a material to seal the hole and the heat sensor from contamination; heating the window laminate; photographing the window laminate using an infrared camera to determine uniformity of heat distribution; placing a heated plate against the exterior surface of the window laminate directly over the position of the replacement heat sensor; measuring an electrical resistance of the replacement heat sensor to confirm proper operation of the replacement heat sensor.

An additive manufactured airframe structure includes a first additive manufactured fuselage segment including a first outer wall that extends in a normal direction from a first end to a second end, and also includes a plurality of reinforcement elements extending from the second end of, and away from, the first outer wall in the normal direction. The airframe structure also includes a second additive manufactured fuselage segment formed separately from the first additive manufactured fuselage segment and including a second outer wall that extends in the normal direction from a first end to a second end, and a plurality of receiving channels extending along the second outer wall. The plurality of reinforcement elements are received in the plurality of receiving channels and link together the first and second additive manufactured fuselage segments.

A method for manufacturing components includes joining a first edge of a thermoplastic-containing first component part and a second edge of a thermoplastic-containing second component part to one another without any overlap. The first and the second edge are interconnected by friction stir welding. Friction stir welding involves rubbing a rotating friction stir welding pin against at least one metal object.

A dissolvable composition is disclosed. The composition includes a first material (e.g., an anode), a second material (e.g., a cathode), and a third material (electrolytic material). The third material is reactive with water to form an electrolyte. The first material and the second material are electrochemically different such that the first material and the second material are capable of galvanic reaction in the presence of water and electrolytes. Also disclosed are tools or other apparatus made from the composition, as well as processes, systems, and apparatus for making and using such compositions, tools, and other apparatus.